Flying machine



Nov. 10, 1931. w. ROBERTS 1,831,139

FLYING MACHINE Filed March 10, 1950 2 Sheets-Sheet 1 5mm WILLIHMRUBERTE W. ROBERTS FLYING MACHINE Filed March 10, 1930 2 Sheets-Sheet 2 Sumo/Mom I WILLIHM RUBERTS- gt z wow; MYQQ Nov. 10, 193 1.

Patented Nov. 10, 1931- 'nmrsssn FST MES wrrnrm nonnnra or'nanen rucx,commencing: i

r yme i Application filed;M a;ph 10, 1930. Serial K01434 574.

. flMy invention relates to flyiing machines andhasfforitsobject toincreaseth is etyof This objectl accomplish byr'en'derling the lift more A or less independent ,of the 1 5 'fiying speed in varying the aeroidynanii c char- 1s ,aglift- ,which at, standstill will be, a;functi on,- of

acteristicswregarding lift and stability; but Without changing the fundamental design qualities of the present-day anemia. j

,lnjacco rdance' with'nly invention I ,place fbec-k ,of-the'lea'ding mam win imnre pathof th Slip -.Str.eam, aseries. of shbrtspan tilta hle .wingsflanfl utili h r acti l i ath ,1 .P' gstram' on, theselastv mentioned ,Wings to create the Slipstream velocity.

ll arrange the tilt-able wings in staggered formation with. a gradually, increasing intermediate gap and I provide controllinjgn eans ffonsimnltaneously varyii ig their inclination from minimum to inaxiniilm incidence, that is from a position of substantially equal incidencetoa position, in which the incidence increases from .wing to Wing.

o incidence. The airplane is in balance-with :the' tiltable wings at maximumrincidence. A forward movement of the centenof-lpressure nat= decreased incidence is i balanced by a lift -on:-ther tail produced by an increase'in the in- E "45 leidence. of the; stabilizer.

I he'invention-enables the pilot to take off and land at steep angles, to maintain levelcontrolled flight' between zero; and, maximum flying speed :and, in the event of engine +tronbleftorileseend ona steep glide at slow .ln=the latter position, the tiltable wings 'eedn e f rqidi m nag r mam P y g lq i r lledrn s -d te 5 he annex d d' Wi "The 'ationar nain arranged on both sides of the jn'selag'ezrlftlie short-span'tiltable Wing's, those on' the left beingindicatedby the nnmerals a hjd 5'8 and those on the right.by' ;th e. niinierals two ailerons formingpart or the stationary main .wing. In 2 andB'isshorgn tlie lever-system for controllingthe position of ethe tiltable .wings. :Separate 'l'eyers indicate'd at 14,15,316 and"'17 are proyided'to -move'zthe opposed tiltable .wings "153ml 9, 6 and-1'0, 7 and 11 and'8 andl2 respectiyely. They are connected,throngh linksf-ZLQ,Q20, 21, 22 and 23 .to handlever 1 8 located ithin easy reach of? thepilot sothat the latter by a displacement of sai'd hand lever :18 can m l aneo s y i epe t nn .Q 'th rious tiltable wings on"botl1"si des of the u lage I I T M al w za r ve singlev w ich: y m n b a r 3 2% e -9 '.fl k.'. v i% ..and

' .27; cpnne e we teb i ersh n a '2 Th sa vers n ve a showman "Figs-: aid1 ,if0 m par of th ab ve d dfi e' sy t b ng .pivo al y con ecte with the'links shown at 22 and'23 and-inlcrnmecl at 32 which may be termed the conthet-ubnlar shafts carrying the tiltable wings and j onrnalle'd suitable bearingsproyided 'forthem inthe sides of the fuselage. 7

At is shown affin, whileat 31,is .s'hoWn h udde As will bere adily nn'derstood from the "foregoing description, by means of the hand- 'by'Fig. 3 the tiltable wings may be rocked v operatively connected with said means to be tionary main wing =4.- this curve is ofgradual ly increasing incidence thus offering a high wind resistance with a resulting high drift. In this position of the wings the maximum lift is produced. 7

.As shown by the broken lines in Fig. 2 and from-the-normal position to a neutral horispeed.

' zontaljposition, which position'they olfer the smallest wind resistance permitting the airplane to move throughthe air at high The tiltable can, of course, be moved to any angular position intermediate the two positions just described correspond- When in the tiltable wings are disposed in j a staggered formation with agradually increasingintermediate gap.

The stabilizer incidence in longitudinalbalance, whereby a very high degree of safety is obtained.

Of course, I do not limit myself to the construction as shown and described allowing for various modifications in the general arrangement .and the details of construction within the skill of those versed in this art.

jposed at the tail end of said fuselage and operatively connected with said means to be adjusted thereby to difi'erent positions corresponding to the positions of said tiltable wings.

2. In an airplane, the combination with the fuselage, of a stationary main wing extending across the front end of said fuselage, tiltable wings journalled on said fuselage in staggered relation so as to form in their normal positions a downwardly curved continuat-ion of said main wing, means for simultaneously varying the positions of said 111g to,the variousreguirements .of li ft and inten rigging shown at 28 being adjusted to various positions simultaneously with the tiltable wings and corresponding thereto will maintain'the airplane atall angles of thereof.

tiltable wings, and a movable stabilizer disposed at the tail end of said fuselage and operatively COIlIleCiGd with said means so that upon a decrease in the incidence of said stabilizer the incident of said stabilizer increases.

3. In an airplane, the combination with ,"the fuselage; of -a stationary main wing extending across the froiifiend of said fuselage, two series of' short-span tiltable wings proqrided either. side of said fuselage in staggered formation so as to form in their normal positions a downwardly curved continuation of said main wing, means for simultaneously varyingathe positions of all said tiltable wings, and a movable stabilizer disposed at the tail end of said fuselage and adjusted thereby to different positions cortending across the front end of said fuselage,

two series pf short-spantiltable wings pro; vi'ded on either side of said fuselage in stag "gered formation so as to form in their normal positions a downwardly curved continudation of said main wing, means for simul tan eou' sly varying the posltions of all said tiltable wings, and a 'movable'stabilizer disposed at the tail end of said fuselage and operatively connected with said means to be adjusted thereby to diiferent positions cor responding to the varied incidence of said tiltable wings, and ailerons disposed at the rear edge of said main wing at the end 5. In an airplane, the combination with the fuselage, of a stationary main wing extending across the front of said fuselage, a series of tiltable wings mounted on either side of said fuselage in staggered formation so as to form in their normal positions a downwardly curved continuation of said main wing, a system of levers operatively connected with said tiltable wings, a. manually operated lever for controlling said levers to thereby simultaneously vary the positions of said tiltable wings, and a movable stabilizer disposed at the tail end of said fuselage and being so connected to said system of levers as to be moved thereby to various positions corresponding to the positions of said tiltable wings.

6. In an airplane, the combination with the fuselage,'of a stationary main wing ex tending across the front of said fuselage, a series of tiltable wings mounted on either side of said fuselage in staggered formation so as to form in their normal positions a downwardly curved continuation of said main wing, a system of levers operatively connected with said tiltable wings, a manually operated lever for controlling said levers to thereby simultaneously vary the positions of said tiltable wings, and a movable stabilizer disposed at the tail end of said fuselage and being so connected to said system of levers as to be moved thereby to various positions corresponding to the positions of said tiltable Wings, the said levers being of successively decreasing length, and ailerons provided at the rear edge of said main wing at both ends thereof.

In testimony whereof I afiix my signature WILLIAM ROBERTS. 

